EFD1000 (Pilot) Airplane Flight Manual Supplement

33 Pages·2009·1.49 MB·English

EFD1000 (Pilot) Airplane Flight Manual Supplement
TABLE OF CONTENTS
1 GENERAL............................................................................................................................................5
1.1 SYSTEM OVERVIEW........................................................................................................................5
2 LIMITATIONS.......................................................................................................................................6
2.1 SOFTWARE VERSIONS....................................................................................................................6
2.2 AIRSPEED LIMITATIONS..................................................................................................................6
2.3 WEIGHT & CENTER OF GRAVITY LIMITS...........................................................................................6
2.4 RSM GPS USAGE.........................................................................................................................6
2.5 GEOGRAPHIC LIMITATION...............................................................................................................6
2.6 PLACARDS AND DECALS.................................................................................................................7
2.7 SEAPLANE OPERATION...................................................................................................................7
3 EMERGENCY AND ABNORMAL PROCEDURES.............................................................................8
3.1 IN-FLIGHT AHRS RESET................................................................................................................8
3.2 PITOT/STATIC SYSTEM BLOCKAGE..................................................................................................8
3.3 LOSS OF EXTERNAL POWER...........................................................................................................9
3.4 POWER OVERRIDE.........................................................................................................................9
3.5 ABNORMAL SHUTDOWN PROCEDURE............................................................................................10
3.6 WARNING, CAUTION, AND ADVISORY SUMMARY.............................................................................10
4 NORMAL PROCEDURES.................................................................................................................12
4.1 EXTERIOR INSPECTION.................................................................................................................12
4.2 BEFORE TAXI CHECKS..................................................................................................................12
4.3 BEFORE TAKE-OFF CHECKS.........................................................................................................12
4.4 SHUTDOWN CHECKS....................................................................................................................12
5 PERFORMANCE...............................................................................................................................13
6 SYSTEM DESCRIPTION...................................................................................................................14
6.1 GENERAL.....................................................................................................................................14
6.2 PILOT CONTROLS.........................................................................................................................14
6.3 PRIMARY FLIGHT INSTRUMENTS....................................................................................................21
6.4 SITUATIONAL AWARENESS MAP DISPLAY......................................................................................27
6.5 MAIN MENU OPERATION...............................................................................................................30
6.6 LIST OF ACRONYMS......................................................................................................................33

DOCUMENT # A-01-179-00 PAGE 3 OF 33 REVISION D
FAA APPROVED
Date: Feb. 3, 2009 © Copyright 2009 Aspen Avionics Inc.
EFD1000 (Pilot) Airplane Flight Manual Supplement

INTENTIONALLY LEFT BLANK

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FAA APPROVED
Date: Feb. 3, 2009 © Copyright 2009 Aspen Avionics Inc.
EFD1000 (Pilot) Airplane Flight Manual Supplement
1 General
1.1 System Overview
The Aspen Avionics’ EFD1000 is a panel-mounted Electronic Flight Instrument System
(EFIS) that presents the pilot with displays of attitude, altitude, indicated airspeed, heading,
rate of turn, and slip/skid information. The system also displays supplemental flight data
such as winds, TAS, OAT, etc., moving maps, pilot-selectable indices (“bugs”), and various
annunciations that increase situational awareness and enhance flight safety. Moving map
situational awareness information is displayed when the unit is connected to compatible
GPS equipment. This aircraft flight manual supplement applies to the EFD1000 “Pilot”
configuration.
The EFD1000 “Pilot” system components include the EFD1000 display head, a Remote
Sensor Module (RSM), and a Configuration Module (CM). The EFD1000 “Pilot” model does
not support display of navigation data from panel-mounted GPS navigators, VOR/Localizer
radios, etc., nor does it integrate with the aircraft autopilot system.
See Section 6 of this Aircraft Flight Manual Supplement for a description of the operation of
the EFD1000 System.

Figure 1 - EFD1000 “Pilot” System Overview

DOCUMENT # A-01-179-00 PAGE 5 OF 33 REVISION D
FAA APPROVED
Date: Feb. 3, 2009 © Copyright 2009 Aspen Avionics Inc.
EFD1000 (Pilot) Airplane Flight Manual Supplement
2 Limitations
2.1 Software Versions
The EFD1000 System must utilize the software versions listed below (or later FAA-approved
versions). The system software version for the Main Application Processor (MAP) and for
the Input-Output Processor (IOP), both of which are contained within the EFD display head,
is displayed via the Main menu SYSTEM STATUS page.
Software Name Version AFM Supplement Revision
IOP SOFTWARE RELEASE 1.0 A-01-179-00 Revision B or C
Or
IOP SOFTWARE RELEASE 1.1 A-01-179-00 Revision C
2.2 Airspeed Limitations
The maximum approved operating airspeed for this system is 264 KTS (304 MPH).
2.3 Weight & Center of Gravity Limits
Installation of the EFD1000 system may result in a small net change to the aircraft empty
weight and associated moment arm. Refer to the revised weight and balance records
carried in the aircraft for details.
2.4 RSM GPS Usage
The EFD1000 RSM GPS is authorized for emergency use only. Position data from the RSM
GPS will ONLY be presented following the loss or failure of a certified external GPS
navigator.

NOTE:
When the RSM GPS is in use, magnetic variation data used by the
basemap is not updated. This can result in misaligned basemap
symbology whenever the external GPS position source is lost and
the aircraft travels far enough to produce a significant change in
the local magnetic variation.

2.5 Geographic Limitation
Like all compass systems, the magnetometer used in the EFD1000 system will experience
degraded performance in the vicinity of the magnetic poles. When the horizontal component
of the earth’s magnetic field is no longer strong enough to provide reliable heading data, the
EFD1000 System will present a “CROSS CHECK ATTITUDE” annunciation, and will
subsequently flag the magnetometer data as invalid, resulting in the annunciated loss of
heading and attitude. Depending on the aircraft latitude and longitude, this effect could be
observed as far away as 750 nm from the magnetic pole. In the Northern Hemisphere, this
equates to operations in the Arctic Islands found north of continental North America
Use of the EFD1000 system for IFR operations with in 750 nautical miles of the Magnetic
Poles, based solely upon the attitude and heading data provided by the EFD1000, is
prohibited.

DOCUMENT # A-01-179-00 PAGE 6 OF 33 REVISION D
FAA APPROVED
Date: Feb. 3, 2009 © Copyright 2009 Aspen Avionics Inc.
EFD1000 (Pilot) Airplane Flight Manual Supplement
2.6 Placards and Decals
The following electronic placard is provided on the EFD1000 display whenever the RSM
GPS is providing position data for the basemap display:
“RSM GPS REVERSION
EMER USE ONLY”
2.7 Seaplane Operation
The EFD1000 system may not be able to align when on water as a function of the wave
action being experienced by the aircraft. When aligning on water, always perform a visual
verification of the attitude reference with a secondary source, such as a mechanical gyro or
the horizon. If the alignment is not successful, it is acceptable to depart under VFR/VMC
and, while maintaining VFR/VMC, perform an AHRS in flight alignment per section 3.

DOCUMENT # A-01-179-00 PAGE 7 OF 33 REVISION D
FAA APPROVED
Date: Feb. 3, 2009 © Copyright 2009 Aspen Avionics Inc.
EFD1000 (Pilot) Airplane Flight Manual Supplement
3 Emergency and Abnormal Procedures
3.1 In-Flight AHRS Reset
ATTITUDE ................................................................Maintain straight and level flight
MENU........................................................................Select “GENERAL SETTINGS” Page
FLY BY VISUAL REFERENCE, OR BY STANDBY INSTRUMENTS
DISCONNECT THE AUTOPILOT
“AHRS: RESET?” LINE SELECT KEY......................PRESS
“AHRS: RESET?” LINE SELECT KEY......................PRESS AGAIN TO CONFIRM RESET
NOTE:
When the EFD1000 AHRS is reset in flight, it performs an
abbreviated initialization.
During the initialization, the aircraft should not be subjected to
excessive turn rates. Typical in-flight initialization will take
approximately 30 seconds, but can take longer if the reset is
initiated while banked or maneuvering.
The AHRS reset is considered complete when the EFD1000
attitude and heading is once again displayed, stable, and correct
with respect to the horizon or standby indicator.

3.2 Pitot/Static System Blockage
CAUTION:
Most light aircraft have only a single pitot and static port available
for flight instrument use. As such, the pitot and static lines used
by the EFD1000 system are shared with those lines used by the
standby airspeed indicator and altimeter. Should these lines
become blocked, such as might occur due to inadvertent icing
encounter, both the standby indicators and the EFD1000
indicators will display erroneous airspeed and/or altitude
information.
Because the EFD1000 uses pitot and static pressures as part of
the ADAHRS solution, loss or corruption of this data, such as
from a line blockage, will impact the accuracy of data output by
the ADAHRS. Affected parameters can include the airspeed,
altitude and attitude information displayed by the EFD1000.
If erroneous pitot or static inputs are detected by the EFD1000,
the EFD1000 will present a “CROSS CHECK ATTITUDE”
annunciation.
A static line blockage will result in altitude remaining fixed and a zero vertical speed despite
aircraft pitch and/or power setting changes. In addition, IAS indications will be incorrect if
the static line is blocked. Errors will typically be noticed in the climb or descent phase of
flight. When descending, ambient pressure increases which will result in the indicated
airspeed reading less than the actual airspeed. The opposite effect will be observed in a
climb. A static line blockage can also affect the EFD1000 attitude indication.

DOCUMENT # A-01-179-00 PAGE 8 OF 33 REVISION D
FAA APPROVED
Date: Feb. 3, 2009 © Copyright 2009 Aspen Avionics Inc.
EFD1000 (Pilot) Airplane Flight Manual Supplement
A pitot line blockage will result in the airspeed indicator behaving like an altimeter when the
aircraft altitude changes, and it would not respond to airspeed changes. A pitot line
blockage can also affect the EFD1000 attitude indication.
If a blocked pitot or static line is suspected, take the following actions:
ALTERNATE STATIC SOURCE...............................SELECT
PITOT HEAT.............................................................ON
3.3 Loss of External Power
In the event that external power to the unit fails, the EFD1000 will automatically switch to its
internal battery.
When operating on internal battery, the display backlight intensity is capped at a value of 70.
SW Version 1.0: Refer to the Main Menu - Power Settings Page when operating on battery
to determine the estimated battery charge remaining.
SW Version 1.1 and subsequent: An annunciation of this operating state and the estimated
battery charge remaining is displayed in the lower portion of the attitude indicator.

CAUTION:
During situations where a high electrical demand is placed on the
aircraft electrical system, electrical transients that cause aircraft
voltage to momentarily drop below 12.5±0.3V (14V Electrical
System) or 25.0±0.6V (28V Electrical System) will cause the EFD
to automatically switch to its internal battery.
This will be accompanied by an “ON BAT” annunciation.
The “ON BAT” annunciation should extinguish shortly after the
electric transient demand goes away. If the “ON BAT”
annunciation does not extinguish then an external power source
failure has most likely occurred
NOTE:
When fully charged the EFD1000 internal battery will allow for
operation for the AHRS, display and RSM emergency GPS for at
least 30 minutes.
3.4 Power Override
In the event that the pilot wishes to override the automatic power configuration of the
equipment:
MENU................................................................................Select “POWER SETTINGS” Page
To switch FROM External Power TO Battery:
“BATTERY” LINE SELECT KEY.......................................PRESS
To switch FROM Battery TO External Power:
“EXT PWR” LINE SELECT KEY.......................................PRESS

DOCUMENT # A-01-179-00 PAGE 9 OF 33 REVISION D
FAA APPROVED
Date: Feb. 3, 2009 © Copyright 2009 Aspen Avionics Inc.
EFD1000 (Pilot) Airplane Flight Manual Supplement
NOTE:
When airborne, if the EFIS input voltage is below the 12.5±0.3V
(14V Electrical System) or 25.0±0.6V (28V Electrical System)
automatic battery transition threshold, and “EXT PWR” is
selected the EFD will automatically transition back to its internal
battery.
3.5 Abnormal Shutdown Procedure
Circuit Breaker...................................................................PULL
REV Button........................................................................HOLD UNTIL DISPLAY BLANKS
3.6 Warning, Caution, and Advisory Summary

WARNINGS
ON BAT (SW Red annunciation presented
Version 1.1 and whenever the EFD1000 is operating
subsequent) on the internal battery. Will be
accompanied by an indication of the
estimated battery charge remaining.
Function FAIL Red annunciation presented
(“X”) whenever the EFD1000 has
determined that the associated
function is invalid or failed and
should not be used. The data is
removed from the display and
replaced by a red “X” over the

affected display feature.

CAUTIONS
CROSS CHECK Amber annunciation presented centered
ATTITUDE in the upper half of the attitude indicator
whenever the EFD1000 AHRS internal
integrity monitor determines that attitude
is potentially degraded. If a CROSS
CHECK ATTITUDE annunciation is
provided the pilot should cross check
attitude, airspeed and altitude
indications.

DOCUMENT # A-01-179-00 PAGE 10 OF 33 REVISION D
FAA APPROVED
Date: Feb. 3, 2009 © Copyright 2009 Aspen Avionics Inc.